WO2000065423A9 - Electronic flight instrument displays - Google Patents
Electronic flight instrument displaysInfo
- Publication number
- WO2000065423A9 WO2000065423A9 PCT/US2000/008766 US0008766W WO0065423A9 WO 2000065423 A9 WO2000065423 A9 WO 2000065423A9 US 0008766 W US0008766 W US 0008766W WO 0065423 A9 WO0065423 A9 WO 0065423A9
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- display
- aircraft
- flight
- instrument system
- electronic
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C23/00—Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
- G01C23/005—Flight directors
Definitions
- the present invention generally relates to the field of electronic flight instrument displays and, in particular, to primary flight displays, moving map displays, and engine parameter displays presented on electronic screens in aircraft cockpits.
- the primary flight display of the prior art consists of an electronic presentation of conventional flight data on a single screen.
- the symbology and information that would have been presented on separate airspeed indicators, altimeters, vertical speed indicators, artificial horizon/flight directors, and, in some cases, directional indicator/horizontal situation indicators, in pre-glass cockpit aircraft are presented together on a single display known as a primary flight display.
- Examples of prior art primary flight displays can be seen in U.S. Patent Nos. 4,860,007, 5,136,301, 5,359,890, 5,412,382, and 5,844,504. All of the prior art primary flight displays essentially involve recreating conventional two-dimensional flight symbology on electronic screens.
- Flight path markers also known as flight path vectors or velocity vectors, are commonplace on Heads Up Displays (HUD). As used on a HUD, flight path markers show the pilot the aircraft's proj ected flight path upon the outside world. Thus, flight path markers are extremely useful for directing an aircraft towards real world objects such as runways and targets. Examples of flight path markers used on HUDs can be seen at U.S. Patent Nos. 4,454,496, 4,554,545, 5,357,263, 5,654,890, and 5,666,111. U.S. Patent No. 5,296,854 shows a flight path marker used with a helmet mounted display rather than a HUD. Flight path markers have also been used on attitude display indicators and primary flight displays.
- HUD Heads Up Displays
- prior art moving maps offer the capability of integrating lightning strike information, traffic information, radar information, data-link weather and traffic information, geographic information, and bit-mapped graphical chart information with the aforementioned navigational symbol database.
- current moving map systems only display information and do not further process information based upon altitude to show the pilot immediate threats to flight safety.
- the present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using a variety of electronic databases, generate intuitive symbols that aid the pilot.
- the present invention also uses various novel algorithms that allows use of data gathered from inexpensive sensors to derive parameters that normally require far more expensive sensors.
- the primary flight display of the present invention discards the old-style two dimensional attitude indicator/flight director symbology in favor of creating a virtual three- dimensional world.
- the display makes use of a terrain database and, optionally, an obstruction database. Terrain and obstructions are presented three-dimensionally as the background of the primary flight display. Navigational symbology is likewise three- dimensional.
- the primary flight display further includes a small, selected- waypoint focused moving map with course line for all-aspect situational awareness.
- aircraft pitch and roll become fixed and the primary flight display becomes a forward looking situational awareness display that intuitively presents the location of terrain, obstructions, and navigational points in three dimensional space in front of the aircraft.
- the moving map of the present invention is similar to prior art moving maps with the exception that it imports aircraft altitude information and displays relevant obstruction and airspace information to the pilot.
- the moving map of the present invention can selectively display only terrain that is above and slightly below current aircraft altitude. In this way, non-critical information is not constantly displayed to distract the pilot, a distinct advantage over moving maps that use bit-mapped cartography.
- obstructions to navigation can be selectively displayed depending upon whether they are a hazard to navigation at a particular aircraft altitude. Airspace limits can be drawn in different colors depending upon whether the aircraft will enter that airspace at its current altitude.
- the engine parameter display of the present invention also includes enhancements that aid pilot situational awareness.
- Engine parameters are displayed as pie wedges with a leading needle and an integral digital display. However, the color of the entire pie wedge is keyed to the relationship of the selected engine parameter to its limit conditions. Normally the pie wedges are green to indicate a normal condition. As the engine parameter reaches its limit, the pie wedge's color changes from green to yellow and then to red to indicate progressively worsening conditions.
- An alternative, bar-type display is particularly useful for comparatively displaying multiple readings from the same type of sensor, such as multiple cylinder head temperature or exhaust gas temperature readings from a multi- cylinder piston engine. As with the pie wedge display, the color of the bar indicates that parameter's condition.
- Figure 1 shows the primary flight display according to the present invention.
- Figure 2 shows the primary flight display according to the present invention with the terrain display turned off.
- Figure 3 shows the moving map display according to the present invention.
- Figure 4 shows the moving map display according to the present invention.
- Figure 5 shows the moving map display according to the present invention.
- Figure 6 shows the engine parameter display according to the present invention.
- Figure 7 shows the methodology for deriving wind according to the present invention.
- the primary flight display includes a heading scale 1 across the top.
- the heading scale is preferably aligned with magnetic North although it can also be aligned with true North.
- the digits 2 of the heading scale are spaced so that, at an aircraft roll angle of zero, the digits conform to the three-dimensional primary flight display background 3.
- the background 3 is generated from terrain elevation and obstruction elevation data stored in electronic memory.
- the heading scale 1 includes a heading carat 4 aligned with the longitudinal axis of the aircraft, and a track pointer 5 aligned with the aircraft's track across the earth.
- a waypoint marker is also displayed on the heading scale at a point that corresponds with the selected waypoint 7. When the selected waypoint 7 is not visible on the background 3, the waypoint marker is replaced by an arrow 6 at either the right-most or left-most limit of the heading scale 1 to indicate the shortest direction of turn to the selected waypoint 7.
- the primary flight display further includes a pitch scale 8 and horizon line 9 that rotate in conjunction with the background 3 according to the aircraft's roll angle.
- the increments on the pitch scale 8 are spaced to conform to the background 3.
- the pitch scale has 5 degree increments with a special reference line 10 located at -3 degrees to correspond to a normal aircraft landing approach angle. Pointer bars 11 at the ends of each numbered pitch scale bar 12 indicate the direction to the horizon.
- the primary flight display further includes an airspeed box 13 and airspeed scale 14.
- the airspeed scale includes colored regions to indicate the relationship of the indicated airspeed to stalling speeds, flap extension speeds, structural cruising speeds, never exceed speeds and other speeds of interest to the pilot.
- the airspeed box 13 and airspeed scale 14 can indicate groundspeed, true airspeed, or indicated/calibrated airspeed. In the preferred embodiment, the airspeed box 13 and airspeed scale 14 indicated/calibrated airspeed. Values such as true airspeed 15, groundspeed 16, normal acceleration or G- force 17, mach number, outside air temperature, and other parameters of interest can be displayed in corner boxes.
- the primary flight display also includes a region for warning messages 18.
- the primary flight display further includes an angle of attack (“AOA") indicator 19.
- AOA angle of attack
- the AOA indicator of the present invention presents its information graphically using a colored bar rather than numerically.
- the AOA indicator of the present invention also monitors aircraft configuration and climb rate to determine the colored bar colors and locations.
- the AOA indicator uses two colors, red and green. The boundary between the two colors represents the AOA for 1.3Ns for that particular configuration.
- the AOA indicator is keyed to display either climb parameters or cruise parameters depending upon the sensed power and rate of climb.
- the AOA indicator of the present invention uses the color green to indicate normal operating AOA's; the color white to indicate operation between max range (cruise parameters) or best rate of climb (climb parameters) AOA and max endurance (cruise parameters) or best angle of climb (climb parameters) AOA; the color yellow to indicate operation between max endurance
- flight with the AOA indicator at the green- white juncture indicates either max range AOA or best rate of climb AOA while flight at the white-yellow juncture indicates flight at max endurance AOA or best angle of climb AOA.
- the yellow-red juncture represents stall onset AOA.
- the primary flight display further includes an altitude box 20 with altitude scale 21.
- Altitude warnings can be set by the pilot and will cause a colored bar to be superimposed upon the altitude scale.
- the preferred embodiment includes two altitude warning modes, altitude hold and decision height.
- Altitude hold mode causes a green bar centered upon the selected altitude to be superimposed upon the altitude scale 21 from 100 feet below the selected altitude to 100 feet above the selected altitude, further causes yellow bars to be superimposed upon the altitude scale 21 from 100 feet below to 300 feet below and 100 feet above to 300 feet above the selected altitude, and further causes red bars to be superimposed upon the altitude scale 21 at all other altitudes.
- the altitude box 20 and altitude scale 21 can display altitude above mean sea level, altitude above ground level, density altitude or pressure altitude. In the preferred embodiment, the altitude box 20 and altitude scale 21 display altitude above mean sea level as adjusted by an altimeter setting 22.
- Altitude related values such as altimeter setting 22, density altitude 23, altitude above ground level 24, altitude alert mode and selected altitude 25, and other parameters of interest can be displayed in corner boxes.
- the primary flight display further includes a vertical speed indicator scale with pointer 26.
- the background of the vertical speed indicator scale is color coded to indicate climb (green) or descent (red).
- a flight path marker 28 appears on the background 3 so as to coincide with the aircraft's actual flight path as projected upon the outside world.
- the flight path marker 28 is displaced laterally parallel to the horizon with respect to the center of the display to account for the difference between aircraft track and heading, and is displaced vertically orthogonally to the horizon to account for aircraft glidepath or climb angle.
- the flight path marker 28 is used in conjunction with a three-dimensional background 3, the flight path marker utility normally associated with a HUD is achieved.
- a bank angle scale 29 is centered upon the flight path marker 28 to display aircraft bank angle. In the preferred embodiment, the bank angle scale 29 disappears at small angles of bank to automatically declutter the display. At very high crab angles (the difference between heading and track) the flight path marker becomes
- a timer 44 is optionally displayed and can display local time, Zulu time, a count-down timer or a count-up timer.
- the primary flight display further includes a full complement of three-dimensional navigation symbology such as highway-in-the-sky boxes 30, three-dimensional runway depictions 7, "tethered balloon” waypoint symbols 42, and "free balloon” waypoint symbols for navigational fixes without elevation data.
- three-dimensional navigation symbology such as highway-in-the-sky boxes 30, three-dimensional runway depictions 7, "tethered balloon” waypoint symbols 42, and "free balloon” waypoint symbols for navigational fixes without elevation data.
- a miniature moving map display 31 is displayed in one corner of the primary flight display to give a vertical perspective of the relationship of the aircraft to the selected waypoint.
- the miniature moving map display 31 displays the identifier 32 and elevation 33 of the selected waypoint along with bearing 34 and distance 35 to that waypoint.
- the map portion of the moving map display 31 includes a range circle 36 with range indicator 37, a waypoint symbol 38 with course line 39.
- the initial point is represented on the miniature moving map by an x symbol 43.
- the miniature aircraft 40 represents the location of the aircraft and includes a projected path line 41 emanating from the center of the miniature aircraft 40. In the preferred embodiment, the projected path displays projected aircraft path up to one minute in the future based upon current flight dynamics. 2.
- the Moving Map Referring now to Figures 3, 4 and 5, the moving map of the present invention is disclosed.
- the moving map of the present invention is similar to other current state of the art moving maps from the standpoint of displaying navigational points from a vertical perspective.
- the moving map of the present invention also imports flight parameters such as altitude, attitude, and true airspeed to generate novel displays that enhance situational awareness.
- the moving map of the present invention is divided into a map section 101 and a data section 102.
- the map section displays standard aerial navigation data such as fixes 103, IFR airports 104, VFR airports 105, NDB's 106, VOR's 107, initial points 108, and flight routes 109.
- the moving map is displayed within a compass rose 110 and can be displayed with the aircraft location 111 offset or centered. Range rings
- Datalink symbology 113 and weather symbology 114 can be imported into the moving map.
- the scale of the moving map is pilot selectable and a scale box 115 presents the currently select map scale.
- Wind information 116 is also presented and includes a graphical wind vector 117.
- a projected path 118 based upon aircraft attitude emanates from the aircraft location 111.
- the preferred embodiment of the present invention also imports aircraft altitude and, making use of the terrain and obstruction databases, displays terrain and obstructions based upon threat level.
- terrain that is within 250 below the aircraft's altitude to the aircraft's altitude is displayed in a dark gray color 119.
- Terrain at or above the aircraft's altitude is displayed in a light gray color 120.
- terrain presented in this manner makes the location of mountains, valleys, flood plains and tributaries readily apparent to the pilot.
- obstructions that are within 250 below the aircraft's altitude to the aircraft's altitude are displayed in a yellow color 121 whereas obstructions at or above the aircraft's altitude are displayed in red 122.
- selective presentation with colors signifying threat level results in a naturally decluttered display that focuses the pilot's attention on true hazards to navigation.
- the data section 102 of the moving map displays various parameters of interest in navigating the aircraft.
- Current position and time 123, next waypoint information 124, destination waypoint information 125, emergency airport information 126, OBS (omni bearing selector) setting and A (automatic) or M (manual) 127, as well as outside air temperature 128 are all displayed.
- Parameters displayed for next waypoint 124, destination waypoint 125 and emergency airport 126 in the preferred embodiment include distance 129, bearing 130, estimated time enroute (ETE) 131, and estimated time of arrival (ETA) 132.
- ETE estimated time enroute
- ETA estimated time of arrival
- the data section 102 also includes a critical message section 133.
- the emergency airport 126 displayed is the nearest airport that meets preset parameters of runway length and IFR/VFR capability.
- OBS 127 is set automatically by selection of a route or waypoint. If a route is selected, OBS is set to the course between waypoints of the route and automatically updates as the aircraft flies over the waypoints. If a normal waypoint (i.e. a fix, NDB, NOR, or airport) is selected without selecting a route, then the OBS is automatically set to the course from aircraft present position to the waypoint. If a runway is selected, then the OBS is automatically set to the runway heading. Whenever a normal waypoint is selected, the pilot can also override the automatic setting and manually set any OBS course desired.
- a normal waypoint i.e. a fix, NDB, NOR, or airport
- an M (manual) is displayed in the OBS setting box 127.
- the automatic OBS setting cannot be manually overridden when a runway is selected.
- a timer 134 is optionally displayed and can display local time, Zulu time, a count- down timer or a count-up timer.
- the engine display 200 consists of various round gauges arranged on a background.
- engine speed 201, manifold pressure 202, fuel flow 203, fuel pressure 204, oil temperature 205, oil pressure 206, volts 207, and amps 208 are displayed in the circular gauge format.
- Other parameters can be displayed, and additional engine displays can be generated to ensure that more complex, multi-engined, or gas-turbine powered aircraft are adequately instrumented.
- Each gauge-type display includes a pie wedge 209 and leading pointer 210.
- the pie wedge is color keyed to correspond to the parameter displayed. For example, if the displayed parameter is in its normal operating range, the pie wedge 209 is preferably filled with green. Likewise, if the displayed parameter is in a cautionary or alarm range, the pie wedge 209 is preferably filled with yellow or red respectively. By changing the color of the entire pie wedge, the pilot's attention is clearly focused on whatever condition is out of its normal parameters.
- the gauge-type displays further include digital labels and readouts 211 and peripheral yellow 212 and red 213 arcs denoting cautionary and alarm parameter ranges.
- An alternative method for displaying engine parameters, and one that is preferred for comparatively showing multiple parameters of the same type, is the bar chart display 214.
- each bar 217 is labeled with the cylinder number 218 and the parameter reading 219.
- Each box further includes a yellow 220 and red 221 line indicating cautionary and alarm ranges for the parameter.
- each bar 217 is colored to represent whether the parameter is in the normal range (green), a cautionary range (yellow) or an alarm range (red).
- This coloring scheme quickly draws the pilots attention to an errant condition and further identifies the exact cylinder having problems.
- the bar representing the highest reading is given a three- dimensional "unpushed button” effect 222 while the bar representing the lowest reading is given a three-dimensional "pushed button” effect 223.
- each bar-graph box 215 and 216 is a recording chart box 224 and 225 showing the history of the parameters over time.
- the boxes in the preferred embodiment show the history of the parameters 10 minutes into the past, although the amount of history displayed can be selected by the pilot or set to a value other than 10 minutes.
- Each recording chart box 224 and 225 includes a yellow 226 and red 227 line indicating cautionary and alarm ranges for the parameter.
- Scale numbers 228 indicate the range displayed, while time numbers 229 indicate the time in history represented by a given horizontal location on the recording chart box 224 and 225.
- Each parameter plotted in a recording chart box 224 and 225 is given its own unique color. Under normal conditions, values for each parameter will remain relatively close as shown in Figure 6.
- Angle of Attack is a very useful parameter due to the fact that for a given configuration, an aircraft's performance is determined primarily by angle of attack. In other words, regardless of weight or altitude, an aircraft will achieve its best rate of climb at a certain AOA, its best angle of climb at another certain AOA, maximum endurance at yet another certain AOA, and so forth. Thus, flying an aircraft by reference to AOA offers a far more precise manner of controlling aircraft performance than by reference to airspeed or other parameters.
- AOA is directly sensed by monitoring sensing vanes attached to the aircraft that align with the relative wind.
- Other devices sense AOA indirectly by monitoring relative static air pressure differences between surface points at various locations on a structure or body exposed to the airstream.
- the preferred embodiment of the present invention uses AOA derived from sensing acceleration in a direction aligned with the vertical axis of the aircraft using an inexpensive accelerometer, the aircraft's indicated, calibrated or equivalent airspeed (IAS, CAS or EAS) from an air data computer system, and the weight of the aircraft derived from a known start weight less the weight of fuel consumed during flight (either totalized from a fuel flow sensor or directly sensed with a fuel quantity sensor) and the weight of items dropped from the aircraft.
- IAS calibrated or equivalent airspeed
- CAS calibrated or equivalent airspeed
- AOA K x W x G / IAS 2
- K is an empirically derived constant unique to any given aircraft
- W is aircraft weight
- G is vertical axis acceleration
- IAS is indicated, calibrated or equivalent airspeed.
- flight path angle flight path angle a ⁇ rmass + AOA x COS(bank) b.
- GPS Global positioning system
- GPS groundspeed and track determined during non-turning flight to the horizontal component of true airspeed and heading.
- an algorithm first determines when an aircraft is flying in a sufficiently straight line that GPS can be reliably used for comparison purposes. If attitude information is available, this determination can be made by referring to aircraft bank angle. A system can also look for periods of relatively constant heading or track to determine when the aircraft is not turning. In non-turning flight, wind is derived as follows (see Figure 7):
- wind speed SQR(wind x 2 + wind y 2 )
- Compute wind direction wind direction + ARCTAN(wind y ⁇ wind x )
- track and groundspeed used by the system for display is re-computed by applying the derived wind to heading and the horizontal component of true airspeed. Wind is continuously determined during periods of non-turning flight. If turning flight is detected, the system remembers the last determined wind and applies that wind to current heading and true airspeed to derive instantaneous track and groundspeed, thus correcting for the inherent deficiencies of GPS track and groundspeed in turning flight. Groundspeed, track and wind derived in this manner has many uses. One such use is determining the correct position of a flight path marker.
- aircraft track determines the location of the flight path marker parallel to the displayed horizon of the primary flight display.
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU64884/00A AU6488400A (en) | 1999-04-01 | 2000-03-31 | Electronic flight instrument displays |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12734199P | 1999-04-01 | 1999-04-01 | |
US60/127,341 | 1999-04-01 |
Publications (3)
Publication Number | Publication Date |
---|---|
WO2000065423A2 WO2000065423A2 (en) | 2000-11-02 |
WO2000065423A3 WO2000065423A3 (en) | 2001-08-23 |
WO2000065423A9 true WO2000065423A9 (en) | 2002-06-20 |
Family
ID=22429614
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2000/008766 WO2000065423A2 (en) | 1999-04-01 | 2000-03-31 | Electronic flight instrument displays |
Country Status (3)
Country | Link |
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US (1) | US6985091B2 (en) |
AU (1) | AU6488400A (en) |
WO (1) | WO2000065423A2 (en) |
Families Citing this family (116)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6907324B2 (en) * | 2000-10-11 | 2005-06-14 | Honeywell International Inc. | Instrument reference flight display system for horizon representation of direction to next waypoint |
FR2817831B1 (en) * | 2000-12-13 | 2003-05-30 | Eads Airbus Sa | STEERING INDICATOR FOR AN AIRCRAFT FOR PROVIDING THE ENGINE PRESSURE RATIO |
US7394402B2 (en) * | 2001-02-02 | 2008-07-01 | Honeywell International Inc. | Tailwind alerting system to prevent runway overruns |
EP1405286B8 (en) * | 2001-07-06 | 2005-11-09 | L-3 Communications Avionics Systems, Inc. | System and method for producing flight pathway |
US7268702B2 (en) * | 2002-01-24 | 2007-09-11 | Toyota Motor Sales, U.S.A., Inc. | Apparatus and methods for providing a flight display in an aircraft |
US20030152264A1 (en) * | 2002-02-13 | 2003-08-14 | Perkins Christopher H. | Method and system for processing stereoscopic images |
US6822624B2 (en) * | 2002-09-10 | 2004-11-23 | Universal Avionics Systems Corporation | Display generation system |
US6782312B2 (en) * | 2002-09-23 | 2004-08-24 | Honeywell International Inc. | Situation dependent lateral terrain maps for avionics displays |
US7158136B2 (en) * | 2002-11-04 | 2007-01-02 | Honeywell International, Inc. | Methods and apparatus for displaying multiple data categories |
FR2847700B1 (en) * | 2002-11-22 | 2005-01-14 | Thales Sa | METHOD OF SYNTHESIZING A THREE DIMENSIONAL INTERVISIBILITY IMAGE |
FR2852689B1 (en) | 2003-03-20 | 2005-06-10 | Airbus France | METHOD AND INDICATOR FOR DISPLAYING ILLUSTRATING MARGIN INFORMATION ON AN AIRCRAFT |
US7039518B2 (en) * | 2003-04-16 | 2006-05-02 | Avidyne Corporation | Computer method and apparatus for aircraft mixture leaning |
US20070203619A1 (en) * | 2003-06-13 | 2007-08-30 | Ingram Michael J | Method and apparatus for calculating engine power and best power |
US8902100B1 (en) | 2008-03-07 | 2014-12-02 | Rockwell Collins, Inc. | System and method for turbulence detection |
EP1687590B1 (en) * | 2003-11-25 | 2013-11-27 | Honeywell International Inc. | Perspective vertical situation display system and method |
JP2005199875A (en) * | 2004-01-16 | 2005-07-28 | Nippon Seiki Co Ltd | Information providing device for vehicle |
JP4622317B2 (en) | 2004-05-31 | 2011-02-02 | 株式会社デンソー | Route guidance apparatus and program |
FR2874258B1 (en) * | 2004-08-10 | 2006-11-03 | Thales Sa | METHOD FOR DISPLAYING MAPPING INFORMATION AND AERONAUTICAL AREAS ON AIRCRAFT SCREEN |
US7075457B1 (en) * | 2004-09-22 | 2006-07-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) | Energy index for aircraft maneuvers |
US7891978B2 (en) * | 2005-01-13 | 2011-02-22 | International Business Machines Corporation | Search and rescue training simulator |
EP1684145B1 (en) * | 2005-01-19 | 2013-05-29 | Airbus Operations | Flight management process for an aircraft |
US6961643B1 (en) | 2005-02-02 | 2005-11-01 | Tru Trak Flight Systems, Inc | System and method for gyro enhanced vertical flight information |
US7330147B2 (en) * | 2005-04-21 | 2008-02-12 | Honeywell International Inc. | System and method for ground proximity warning with enhanced obstacle depiction |
FI117576B (en) * | 2005-04-29 | 2006-11-30 | Tracker Oy | Procedure for displaying objects to be positioned on a positioning equipment display box, positioning equipment and application |
US7908078B2 (en) * | 2005-10-13 | 2011-03-15 | Honeywell International Inc. | Perspective-view visual runway awareness and advisory display |
US7471214B2 (en) * | 2005-10-13 | 2008-12-30 | Honeywell International Inc. | Intuitive wind velocity and direction presentation |
US7876238B2 (en) * | 2005-12-22 | 2011-01-25 | The Boeing Company | Methods and systems for displaying procedure information |
US8271150B2 (en) * | 2005-12-22 | 2012-09-18 | The Boeing Company | Methods and systems for displaying enroute moving maps |
US8200416B2 (en) * | 2005-12-22 | 2012-06-12 | The Boeing Company | Methods and systems for controlling display of en-route maps |
US7352292B2 (en) * | 2006-01-20 | 2008-04-01 | Keith Alter | Real-time, three-dimensional synthetic vision display of sensor-validated terrain data |
US7928862B1 (en) * | 2006-01-30 | 2011-04-19 | Rockwell Collins, Inc. | Display of hover and touchdown symbology on head-up display |
US7689326B2 (en) * | 2006-02-02 | 2010-03-30 | Honeywell International Inc. | Heading awareness symbology for track centered primary flight displays |
US7295135B2 (en) * | 2006-02-06 | 2007-11-13 | Trutrak Flight Systems, Inc. | Flight information system |
FR2897840B1 (en) * | 2006-02-27 | 2009-02-13 | Eurocopter France | METHOD AND DEVICE FOR PROCESSING AND VISUALIZING PILOTAGE INFORMATION OF AN AIRCRAFT |
US7508322B1 (en) * | 2006-03-03 | 2009-03-24 | Rockwell Collins, Inc. | Large error to desired path correction indicator |
US8596373B2 (en) * | 2006-03-10 | 2013-12-03 | Deere & Company | Method and apparatus for retrofitting work vehicle with blade position sensing and control system |
US20070213906A1 (en) * | 2006-03-13 | 2007-09-13 | Deere & Company, A Delaware Corporation | Work vehicle software application display management system and associated method |
US7561067B2 (en) * | 2006-03-30 | 2009-07-14 | Japan Aerospace Exploration Agency | Airspeed / wind speed measurement device for aircraft, and display device for same |
US8032267B1 (en) | 2006-04-03 | 2011-10-04 | Honeywell International Inc. | Aviation navigational and flight management systems and methods with emergency landing guidance and radar vectoring |
US7885733B1 (en) | 2006-04-03 | 2011-02-08 | Honeywell International Inc. | Aviation navigational and flight management systems and methods utilizing radar vectoring |
US8164485B2 (en) * | 2006-04-13 | 2012-04-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | System and method for aiding pilot preview, rehearsal, review, and real-time visual acquisition of flight mission progress |
US7765061B1 (en) * | 2006-05-18 | 2010-07-27 | Rockwell Collins, Inc. | Flight display system with enhanced temporal depiction of navigation information |
US20080004756A1 (en) * | 2006-06-02 | 2008-01-03 | Innovative Solutions & Support, Inc. | Method and apparatus for display of current aircraft position and operating parameters on a graphically-imaged chart |
US8271191B2 (en) * | 2006-06-26 | 2012-09-18 | Honeywell International Inc. | Method of detecting erroneous GPS ground speed on ground |
FR2903787B1 (en) * | 2006-07-11 | 2008-11-14 | Thales Sa | DEVICE FOR GENERATING THE EMERGENCY FUNCTION IN A HIGH HEAD VIEWFINDER |
US8185301B1 (en) * | 2006-07-26 | 2012-05-22 | Honeywell International Inc. | Aircraft traffic awareness system and methods |
WO2008077105A1 (en) * | 2006-12-19 | 2008-06-26 | Embedded Control Systems | Method and apparatus to facilitate providing a synthetic view of terrain for use in a moving vehicle |
US10168179B2 (en) * | 2007-01-26 | 2019-01-01 | Honeywell International Inc. | Vehicle display system and method with enhanced vision system and synthetic vision system image display |
FR2920580B1 (en) * | 2007-08-31 | 2010-09-03 | Thales Sa | METHOD FOR SIMPLIFYING THE DISPLAY OF STATIONARY ELEMENTS OF AN EMBEDDED DATA BASE |
US20090125222A1 (en) * | 2007-11-13 | 2009-05-14 | Honeywell International, Inc. | Flight plan comparison system and method |
FR2924212B1 (en) * | 2007-11-23 | 2010-02-26 | Thales Sa | VIRTUAL CONTROL PANEL OF AERONAUTICAL ATTITUDE PLANTS |
US9091545B2 (en) * | 2007-11-27 | 2015-07-28 | Florida Institute For Human And Machine Cognition, Inc. | Motion-resolving hover display |
US7869943B1 (en) | 2007-12-21 | 2011-01-11 | Honeywell International Inc. | Flight management systems and methods for use with an aerial vehicle |
US20090201287A1 (en) * | 2008-02-07 | 2009-08-13 | Honeywell International Inc. | System and method of adaptively filtering parametric data for display |
US9864055B1 (en) | 2014-03-12 | 2018-01-09 | Rockwell Collins, Inc. | Weather radar system and method for detecting a high altitude crystal cloud condition |
US8339284B2 (en) * | 2008-03-11 | 2012-12-25 | Honeywell International Inc. | Method and apparatus for displaying flight path information in rotocraft |
US8035547B1 (en) | 2008-03-17 | 2011-10-11 | Garmin Switzerland Gmbh | System and method of assisted aerial navigation |
US8457889B2 (en) * | 2008-03-31 | 2013-06-04 | Honeywell International Inc. | Waypoint display system and method |
US8392039B2 (en) * | 2008-05-29 | 2013-03-05 | Honeywell International Inc. | Method and system displaying crosswind correction for approach to a runway |
US9829341B1 (en) * | 2008-06-26 | 2017-11-28 | Rockwell Collins, Inc. | System and method for providing flight cues for the navigation function required time of arrival (RTA) |
US8099201B1 (en) * | 2008-08-29 | 2012-01-17 | Rockwell Collins, Inc. | Vertical profile display with enhanced temporal depiction of navigation information |
US7868785B1 (en) * | 2008-08-29 | 2011-01-11 | Rockwell Collins, Inc. | Ownship symbol for enhanced situation awareness |
US8160755B2 (en) * | 2008-09-30 | 2012-04-17 | Honeywell International Inc. | Displaying air traffic symbology based on relative importance |
US8188890B2 (en) * | 2008-11-13 | 2012-05-29 | Honeywell International Inc. | Systems and methods for enhancing obstacles and terrain profile awareness |
US20100131126A1 (en) * | 2008-11-21 | 2010-05-27 | Honeywell International Inc. | System and display element for displaying waypoint markers with integrated altitude constraint information |
US20100179712A1 (en) * | 2009-01-15 | 2010-07-15 | Honeywell International Inc. | Transparent vehicle skin and methods for viewing vehicle systems and operating status |
US8554393B2 (en) * | 2009-09-25 | 2013-10-08 | Honeywell International Inc. | Airspace awareness enhancement system and method |
US8531315B2 (en) * | 2009-10-26 | 2013-09-10 | L-3 Communications Avionics Systems, Inc. | System and method for displaying runways and terrain in synthetic vision systems |
US9053630B2 (en) * | 2010-02-17 | 2015-06-09 | The Boeing Company | Methods and systems for depicting a data driven minimum safe altitude |
US8374776B2 (en) * | 2010-03-31 | 2013-02-12 | The Boeing Company | Methods and apparatus for indicating a relative altitude in one or more directions |
EP2559017A2 (en) * | 2010-04-12 | 2013-02-20 | Flight Focus Pte. Ltd. | Moving map display |
US8649915B2 (en) | 2010-05-28 | 2014-02-11 | The Clear View Group Llc | Method and apparatus to facilitate providing a synthetic view of terrain for use in a moving vehicle |
US8290639B2 (en) * | 2010-11-04 | 2012-10-16 | The Boeing Company | Managing control surfaces for an aircraft |
US8463534B2 (en) | 2010-11-13 | 2013-06-11 | The Boeing Company | Position/time synchronization of unmanned air vehicles for air refueling operations |
US9153137B2 (en) * | 2010-12-13 | 2015-10-06 | The Boeing Company | Temporally based weather symbology |
FR2977948B1 (en) * | 2011-07-12 | 2014-11-07 | Eurocopter France | AUTOMATICALLY CONTROLLED AIRCRAFT AIRCRAFT COMPRISING AT LEAST ONE PROPELLANT PROPELLER, AUTOMATICALLY CONTROLLED AIRCRAFT DEVICE |
US9019146B1 (en) | 2011-09-27 | 2015-04-28 | Rockwell Collins, Inc. | Aviation display depiction of weather threats |
US9823347B1 (en) | 2014-03-12 | 2017-11-21 | Rockwell Collins, Inc. | Weather radar system and method for high altitude crystal warning interface |
GB2499776A (en) * | 2011-11-17 | 2013-09-04 | Thermoteknix Systems Ltd | Projecting secondary information into an optical system |
US8875568B2 (en) | 2012-06-14 | 2014-11-04 | Argen Aviation, Inc. | Relative wind display and landing aid |
US9309004B2 (en) * | 2012-09-21 | 2016-04-12 | Merlin Technology, Inc. | Centripetal acceleration determination, centripetal acceleration based velocity tracking system and methods |
FR2998873B1 (en) * | 2012-11-30 | 2016-10-14 | Airbus | AID FOR THE CONTROL OF AN AIRCRAFT IN THE SITUATION |
US9592921B2 (en) * | 2013-03-11 | 2017-03-14 | Honeywell International Inc. | Graphical representation of in-flight messages |
US10203219B2 (en) * | 2013-04-04 | 2019-02-12 | Sky Motion Research Ulc | Method and system for displaying nowcasts along a route on a map |
US10324231B2 (en) | 2013-04-04 | 2019-06-18 | Sky Motion Research, Ulc | Method and system for combining localized weather forecasting and itinerary planning |
US10495785B2 (en) | 2013-04-04 | 2019-12-03 | Sky Motion Research, Ulc | Method and system for refining weather forecasts using point observations |
US10330827B2 (en) | 2013-04-04 | 2019-06-25 | Sky Motion Research, Ulc | Method and system for displaying weather information on a timeline |
TWI631361B (en) | 2013-06-26 | 2018-08-01 | 加拿大商天勢研究無限公司 | Method and system for displaying weather information on a timeline |
US9760696B2 (en) * | 2013-09-27 | 2017-09-12 | Excalibur Ip, Llc | Secure physical authentication input with personal display or sound device |
US9535158B1 (en) | 2013-11-21 | 2017-01-03 | Rockwell Collins, Inc. | Weather radar system and method with fusion of multiple weather information sources |
US9599707B1 (en) * | 2014-01-23 | 2017-03-21 | Rockwell Collins, Inc. | Weather radar system and method with path attenuation shadowing |
TWI593942B (en) * | 2014-04-07 | 2017-08-01 | 天勢研究無限公司 | Methods for generating a map comprising weather forecasts or nowcasts and ground navigation devices and non-transitory computer readable medium thereof |
TWI639811B (en) * | 2014-04-07 | 2018-11-01 | 加拿大商天勢研究無限公司 | Methods for generating a map comprising weather forecasts or nowcasts and ground navigation devices and non-transitory computer readable medium thereof |
US9810770B1 (en) | 2014-07-03 | 2017-11-07 | Rockwell Collins, Inc. | Efficient retrieval of aviation data and weather over low bandwidth links |
US9881504B2 (en) | 2014-07-17 | 2018-01-30 | Honeywell International Inc. | System and method of integrating data link messages with a flight plan |
US10330493B2 (en) | 2014-12-03 | 2019-06-25 | Honeywell International Inc. | Systems and methods for displaying position sensitive datalink messages on avionics displays |
US9979934B1 (en) * | 2015-01-06 | 2018-05-22 | Rockwell Collins, Inc. | Automated weather sensing system and method using cameras |
US9869766B1 (en) | 2015-01-28 | 2018-01-16 | Rockwell Collins, Inc. | Enhancement of airborne weather radar performance using external weather data |
WO2016149039A1 (en) * | 2015-03-17 | 2016-09-22 | Sikorsky Aircraft Corporation | Trajectory control of a vehicle |
BR112017021458B1 (en) * | 2015-04-07 | 2022-12-20 | Aspen Avionics, Inc. | SYSTEM AND METHOD FOR INDICATION OF ANGLE OF ATTACK WITHOUT DEDICATED SENSORS AND AIRCRAFT INFORMATION |
WO2016191320A1 (en) * | 2015-05-22 | 2016-12-01 | Tiger Century Aircraft, Inc. | Aircraft energy state awareness display systems and methods |
EP3104125B1 (en) * | 2015-06-12 | 2018-10-31 | Airbus Defence and Space GmbH | Aircraft navigation system and method for aircraft navigation |
US10809375B1 (en) | 2015-09-14 | 2020-10-20 | Rockwell Collins, Inc. | Radar system and method for detecting hazards associated with particles or bodies |
US10302815B1 (en) | 2015-10-01 | 2019-05-28 | Rockwell Collins, Inc. | System and method of integrating global convective weather |
US9911345B2 (en) * | 2016-02-24 | 2018-03-06 | Honeywell International Inc. | System and method for detecting misaligned stationary objects |
US10494108B1 (en) | 2016-05-17 | 2019-12-03 | Rockwell Collins, Inc. | System and method for providing icing condition warnings |
CA3029131A1 (en) * | 2016-06-29 | 2018-01-04 | L-3 Technologies Avionic Products | Intuitive display of angle of attack guidance on aircraft attitude indicator |
US9969503B2 (en) * | 2016-07-21 | 2018-05-15 | Rockwell Collins, Inc. | Head-up display (HUD) stall recovery symbology |
FR3060740B1 (en) * | 2016-12-20 | 2019-05-10 | Thales | METHOD FOR GRAPHIC MANAGEMENT OF A TANGLE SCALE IN AN AIRCRAFT VISUALIZATION SYSTEM |
US10094682B2 (en) * | 2017-02-22 | 2018-10-09 | Honeywell International Inc. | Cockpit display systems and methods for performing glide slope validation processes during instrument landing system approaches |
US10332413B2 (en) * | 2017-05-30 | 2019-06-25 | Honeywell International Inc. | System and method for adjusting the correlation between a visual display perspective and a flight path of an aircraft |
US10640230B2 (en) | 2018-04-04 | 2020-05-05 | Jurgen R. Ihns | Cockpit pressurization and oxygen warning system |
US11345482B2 (en) | 2018-10-18 | 2022-05-31 | Milton Academy | Aeronautical display system and method |
US20210166570A1 (en) * | 2019-11-29 | 2021-06-03 | Bombardier Inc. | Aircraft display system and method |
US11577828B2 (en) * | 2020-04-30 | 2023-02-14 | Lockheed Martin Corporation | Power display for compound aircraft using shared engine torque |
CN112347556B (en) * | 2020-09-28 | 2023-12-01 | 中测新图(北京)遥感技术有限责任公司 | Airborne LIDAR aerial photography design configuration parameter optimization method and system |
Family Cites Families (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3686936A (en) * | 1970-02-11 | 1972-08-29 | Charles H Daudt Jr | Method and apparatus for detecting stall buffet |
US4534000A (en) * | 1975-08-29 | 1985-08-06 | Bliss John H | Inertial flight director system |
US4247843A (en) * | 1978-08-23 | 1981-01-27 | Sperry Corporation | Aircraft flight instrument display system |
US4305057A (en) * | 1979-07-19 | 1981-12-08 | Mcdonnell Douglas Corporation | Concave quadratic aircraft attitude reference display system |
FR2487505A1 (en) * | 1980-07-23 | 1982-01-29 | Dassault Avions | DEVICE FOR ASSISTING THE CONTROL OF AN AIR VEHICLE |
US4554545A (en) * | 1980-10-30 | 1985-11-19 | Mcdonnell Douglas Corporation | Conformal head-up display |
US4454496A (en) * | 1980-10-30 | 1984-06-12 | Mcdonald Douglas Corporation | Conformal head-up display |
US4559822A (en) * | 1982-04-23 | 1985-12-24 | Huntington Morgan G | Aircraft potential of wing lift instrument and method |
US4860007A (en) * | 1988-01-15 | 1989-08-22 | The Boeing Company | Integrated primary flight display |
US5003305A (en) * | 1988-10-24 | 1991-03-26 | The Boeing Company | Apparatus and method for displaying aircraft flight path angle on an attitude display indicator |
US5136301A (en) * | 1989-08-30 | 1992-08-04 | Rockwell International Corporation | Primary flight display system having a vertical linear altimeter |
DE3930862A1 (en) * | 1989-09-15 | 1991-03-28 | Vdo Schindling | METHOD AND DEVICE FOR PRESENTING AIRPORT INFORMATION |
DE4109016C2 (en) * | 1991-03-20 | 1994-10-06 | Dornier Luftfahrt | Display instrument for aircraft to display the flight position, in particular the roll and pitch position or the flight path angle |
CA2060406C (en) * | 1991-04-22 | 1998-12-01 | Bruce Edward Hamilton | Helicopter virtual image display system incorporating structural outlines |
US5150117A (en) * | 1991-04-22 | 1992-09-22 | United Technologies Corporation | Power management symbology display system |
US5198812A (en) * | 1992-03-04 | 1993-03-30 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft attitude indicator display |
US5343395A (en) * | 1992-08-26 | 1994-08-30 | Watts Alan B | Aircraft landing guidance system and method |
US5359890A (en) * | 1993-05-04 | 1994-11-01 | Honeywell Inc. | Integrated electronic primary flight display |
US5459666A (en) * | 1993-12-14 | 1995-10-17 | United Technologies Corporation | Time and fuel display |
US5412382A (en) * | 1993-12-30 | 1995-05-02 | Honeywell Inc. | Integrated electronic primary flight display |
US5654890A (en) * | 1994-05-31 | 1997-08-05 | Lockheed Martin | High resolution autonomous precision approach and landing system |
US5595357A (en) * | 1994-07-05 | 1997-01-21 | The B. F. Goodrich Company | Aircraft stall warning system |
FR2730841B1 (en) * | 1995-02-17 | 1997-04-25 | Sextant Avionique | AIRCRAFT MONITORING AND GUIDANCE METHOD AND DEVICE FOR PRECISION LANDING |
US5668542A (en) * | 1995-07-03 | 1997-09-16 | The United States Of America As Represented By The Secretary Of The Air Force | Color cockpit display for aircraft systems |
US6028536A (en) * | 1995-11-16 | 2000-02-22 | Northrop Grumman Corporation | Integrated flight control indicator |
US5844504A (en) * | 1997-07-22 | 1998-12-01 | Rockwell International | Compressed circle flight display |
US5978715A (en) * | 1997-10-15 | 1999-11-02 | Dassault Aviation | Apparatus and method for aircraft display and control |
US6271769B1 (en) * | 1997-12-02 | 2001-08-07 | Proprietary Software Systems, Inc. | Apparatus and method for measuring and displaying angular deviations from angle of zero lift for air vehicles |
US6567014B1 (en) * | 1998-11-05 | 2003-05-20 | Rockwell Collins, Inc. | Aircraft head up display system |
US6131055A (en) * | 1998-12-11 | 2000-10-10 | The Boeing Company | Aircraft non-normalized angle-of-attack indicating system |
US6486799B1 (en) * | 1999-07-19 | 2002-11-26 | The University Of West Florida | Computer based human-centered display system |
-
2000
- 2000-03-31 WO PCT/US2000/008766 patent/WO2000065423A2/en active Application Filing
- 2000-03-31 AU AU64884/00A patent/AU6488400A/en not_active Abandoned
-
2003
- 2003-04-22 US US10/420,602 patent/US6985091B2/en not_active Expired - Lifetime
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US6985091B2 (en) | 2006-01-10 |
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